HARTZELL PROPELLER INC.

Transcription

1 HARTZELL PROPELLER INC. One Propeller Place Piqua, Ohio U.S.A. Telephone: Fax: MANUAL REVISION TRANSMITTAL Manual ( ) Propeller Owner's Manual and Logbook REVISION 13 dated June 2015 Attached is a copy of Revision 13 to Hartzell Manual. Page Control Chart for Revision 13: Remove Page No. COVER/INSIDE COVER Insert Page No. COVER/INSIDE COVER REVISION HIGHLIGHTS REVISION HIGHLIGHTS pages 5 thru 8 pages 5 thru 8 LIST OF EFFECTIVE PAGES LIST OF EFFECTIVE PAGES pages 23 and 24 pages 23 and 24 TABLE OF CONTENTS TABLE OF CONTENTS pages 27 and 28 pages 27 and 28 pages 31 and 32 pages 31 and 32 INTRODUCTION INTRODUCTION pages 1-5 thru 1-14 pages 1-5 thru 1-14 INSTALLATION AND REMOVAL INSTALLATION AND REMOVAL pages 3-1 thru 3-4 pages 3-1 thru 3-4 pages 3-11 and 3-12 pages 3-11 and 3-12 pages 3-17 thru 3-68 pages 3-17 thru 3-70 INSPECTION AND CHECK INSPECTION AND CHECK pages 5-23 and 5-24 pages 5-23 and 5-24 MAINTENANCE PRACTICES MAINTENANCE PRACTICES pages 6-9 and 6-10 pages 6-9 and 6-10 This page may be discarded after proper filing of the revision. Page 1 of 2

2 Page Control Chart for Revision 13, continued: Remove Page No. Insert Page No. NOTE 1: When the manual revision has been inserted in the manual, make a record of the information required on the Record of Revisions page in this manual. NOTE 2: Pages distributed in this revision may include pages from previous revisions if they are on the opposite side of revised page. This is done as a convenience to those users who wish to print a two-sided copy of the new revision. Page 2 of 2

3 Manual No Revision 13 June 2015 Propeller Owner's Manual and Logbook Series: HC-B3( )( )-2( ) HC-B3( )( )-3( ) HC-B3( )( )-5( ) HC-B3TF-7( ) HC-B4( )( )-3( ) HC-B4( )( )-5( ) HC-B5M( )-2( ) HC-B5M( )-3( ) HC-B5M( )-5( ) HC-A3(V,MV)F-7( ) Steel Hub Turbine Propellers with Aluminum Blades Hartzell Propeller Inc. One Propeller Place Piqua, OH U.S.A. Ph: (Hartzell Propeller Inc.) Ph: (Product Support) Product Support Fax:

4 Propeller Owner's Manual 1984, 1992, 1994, 1997, 1999, 2001, 2002, 2006, 2009, 2011, 2012, 2013, 2015 Hartzell Propeller Inc. - All rights reserved COVER Page 2

5 Propeller Owner's Manual REVISION 13 HIGHLIGHTS Revision 13, dated June 2015, incorporates the following: COVER Revised to match the manual revision REVISION HIGHLIGHTS Revised to match the manual revision LIST OF EFFECTIVE PAGES Revised to match the manual revision TABLE OF CONTENTS Revised to match the manual revision INTRODUCTION Revised to add the use of safety cable Revised the section, "Reference Publications" Made other language/format changes INSTALLATION AND REMOVAL Revised to add the use of safety cable, where applicable Revised the section, "Installing HC-B(3, 4)( )W-3( ) Propeller on the Aircraft Engine" to include compliance with GE Aviation Service Bulletin H on Thrush aircraft models S2R-H80 or S2RHG-H80 Made other language/format changes INSPECTION AND CHECK Revised the illustration, "Turbine Engine Overtorque Limits" MAINTENANCE PRACTICES Revised the section, "Carbon Block Assemblies" REVISION HIGHLIGHTS Page 5

6 Propeller Owner's Manual (This page is intentionally blank.) REVISION HIGHLIGHTS Page 6

7 1. Introduction A. General Propeller Owner's Manual REVISION HIGHLIGHTS (1) This is a list of current revisions that have been issued against this manual. Please compare it to the RECORD OF REVISIONS page to make sure that all revisions have been added to the manual. B. Components (1) Revision No. indicates the revisions incorporated in this manual. (2) Issue Date is the date of the revision. (3) Comments indicates the level of the revision. (a) New Issue is a new manual distribution. The manual is distributed in its entirety. All the page revision dates are the same and no change bars are used. (b) Reissue is a revision to an existing manual that includes major content and/or major format changes. The manual is distributed in its entirety. All the page revision dates are the same and no change bars are used. (c) Major Revision is a revision to an existing manual that includes major content or minor content changes over a large portion of the manual. The manual is distributed in its entirety. All the page revision dates are the same, but change bars are used to indicate the changes incorporated in the latest revision of the manual. (d) Minor Revision is a revision to an existing manual that includes minor content changes to the manual. Only the revised pages of the manual are distributed. Each page retains the date and the change bars associated with the last revision to that page. REVISION HIGHLIGHTS Page 7

8 Propeller Owner's Manual Revision No. Issue Date Comments Revision 5 Oct/99 Reissue Revision 6 Mar/01 Minor Revision Revision 7 Oct/02 Minor Revision Revision 8 Dec/06 Minor Revision Revision 9 Aug/09 Minor Revision Revision 10 Jun/11 Minor Revision Revision 11 Jul/12 Minor Revision Revision 12 Mar/13 Minor Revision Revision 13 Jun/15 Minor Revision REVISION HIGHLIGHTS Page 8

9 Propeller Owner's Manual LIST OF EFFECTIVE PAGES Chapter Page Revision Date Cover Cover and Inside Cover Message 1 thru 4 Rev. 6 Mar/01 Revision Highlights 5 thru 8 Record of Revisions 9 and 10 Rev. 6 Mar/01 Record of Temporary Revisions 11 and 12 Rev. 6 Mar/01 Service Documents List 13 and 14 Rev. 11 Jul/12 Airworthiness Limitations 15 thru 22 Rev. 10 Jun/11 List of Effective Pages 23 and 24 Table of Contents 25 and 26 Rev. 12 Mar/13 Table of Contents 27 Table of Contents 28 thru 31 Rev. 12 Mar/13 Table of Contents 32 Table of Contents 33 and 34 Rev. 12 Mar/13 Introduction 1-1 thru 1-5 Rev. 12 Mar/13 Introduction 1-6 thru 1-13 Introduction 1-14 thru 1-16 Rev. 11 Jul/12 Description and Operation 2-1 Rev. 12 Mar/13 Description and Operation 2-2 Rev. 11 Jul/12 Description and Operation 2-3 Rev. 10 Jun/11 Description and Operation 2-4 Rev. 7 Oct/02 Description and Operation 2-5 Rev. 11 Jul/12 Description and Operation 2-6 thru 2-19 Rev. 7 Oct/02 Description and Operation 2-20 Rev. 11 Jul/12 Description and Operation 2-21 thru 2-27 Rev. 7 Oct/02 Description and Operation 2-28 and 2-29 Rev. 11 Jul/12 Description and Operation 2-30 and 2-31 Rev. 10 Jun/11 Description and Operation 2-32 thru 2-35 Rev. 7 Oct/02 Description and Operation 2-36 thru 2-38 Rev. 12 Mar/13 Installation and Removal 3-1 thru 3-4 Installation and Removal 3-5 Rev. 7 Oct/02 Installation and Removal 3-6 thru 3-10 Rev. 11 Jul/12 Installation and Removal 3-11 Rev. 8 Dec/06 Installation and Removal 3-12 LIST OF EFFECTIVE PAGES Page 23

10 Propeller Owner's Manual LIST OF EFFECTIVE PAGES Chapter Page Revision Date Installation and Removal 3-13 thru 3-16 Rev. 11 Jul/12 Installation and Removal 3-17 and 3-18 Installation and Removal 3-19 Rev. 11 Jul/12 Installation and Removal 3-20 thru 3-23 Installation and Removal 3-24 and 3-25 Rev. 11 Jul/12 Installation and Removal 3-26 thru 3-29 Installation and Removal 3-30 Rev. 11 Jul/12 Installation and Removal 3-31 thru 3-70 Testing and Troubleshooting 4-1 and 4-2 Rev. 12 Mar/13 Testing and Troubleshooting 4-3 Rev. 7 Oct/02 Testing and Troubleshooting 4-4 Rev. 12 Mar/13 Testing and Troubleshooting 4-5 thru 4-10 Rev. 7 Oct/02 Testing and Troubleshooting 4-11 and 4-12 Rev. 10 Jun/11 Inspection and Check 5-1 Rev. 12 Mar/13 Inspection and Check 5-2 thru 5-19 Rev. 11 Jul/12 Inspection and Check 5-20 and 5-21 Rev. 12 Mar/13 Inspection and Check 5-22 Rev. 11 Jul/12 Inspection and Check 5-23 Inspection and Check 5-24 thru 5-34 Rev. 11 Jul/12 Maintenance Practices 6-1 and 6-2 Rev. 12 Mar/13 Maintenance Practices 6-3 Rev. 11 Jul/12 Maintenance Practices 6-4 Rev. 6 Mar/01 Maintenance Practices 6-5 thru 6-8 Rev. 11 Jul/12 Maintenance Practices 6-9 Maintenance Practices 6-10 Rev. 11 Jul/12 Maintenance Practices 6-11 Rev. 12 Mar/13 Maintenance Practices 6-12 thru 6-22 Rev. 11 Jul/12 Maintenance Practices 6-23 and 6-24 Rev. 12 Mar/13 Anti-ice and De-ice Systems 7-1 thru 7-8 Rev. 12 Mar/13 Records 8-1 thru 8-4 Rev. 5 Oct/99 LIST OF EFFECTIVE PAGES Page 24

11 Propeller Owner's Manual CONTENTS Page 3. Propeller Assembly Installation A. Precautions B. Installing HC-B(3, 5)( )( )-2( ) Propeller on the Aircraft Engine C. Installing HC-B(3,4,5)( )(A,N,P)-3( ) Propeller on the Aircraft Engine D. Installing HC-B(3,4)( )W-3( ) Propeller on the Aircraft Engine E. Installing HC-B(3,4)( )( )-5( ) Propeller, with a One-piece Spinner Mounting Plate, on the Aircraft Engine F. Installing HC-B(3,4,5)( )( )-5( ) Propeller, with a Two-piece Spinner Mounting Plate, on the Aircraft Engine G. Installing HC-( )3( )( )-7( ) Propeller on the Allison Engine Spinner Dome Installation Post-Installation Checks Spinner Dome Removal Propeller Assembly Removal A. Removal of HC-B(3,5)( )( )-2( ) Propellers B. Removal of HC-B(3,4,5)( )(A,N,P)-3( ) Propellers C. Removal of HC-B(3,4)( )W-3( ) Propellers D. Removal of HC-B(3,4,5)( )( )-5( ) Propellers E. Removal of HC-( )3( )( )-7( ) Propellers F. Removal of Beta Valve Assembly for HC-( )3( )( )-7( ) Propellers TABLE OF CONTENTS Page 27

12 Propeller Owner's Manual CONTENTS Page TESTING AND TROUBLESHOOTING Operational Tests A. Initial Run-Up B. Post-Run Check C. Maximum RPM (Static) Hydraulic Low Pitch Stop Check D. Feathering Pitch Stop Adjustment E. Start Lock Unit Adjustment F. Propeller Ice Protection System Troubleshooting A. Hunting and Surging B. Engine Speed Varies with Airspeed C. Loss of Propeller Control D. Failure to Feather (or feathers slowly) E. Failure to Unfeather F. Start Lock Units Fail to Latch on Shutdown (-2, -5 and some -3 Models) G. Vibration H. Propeller Overspeed I. Propeller Underspeed J. Oil or Grease Leakage INSPECTION AND CHECKS Pre-Flight Checks Post-Flight Checks Operational Checks Required Periodic Inspections and Maintenance A. Periodic Inspections B. Periodic Maintenance C. Compliance Inspections D. Airworthiness Limitations E. Overhaul Periods TABLE OF CONTENTS Page 28 Rev. 12 Mar/13

13 Propeller Owner's Manual RECORDS Introduction Record Keeping A. Information to be Recorded LIST OF ILLUSTRATIONS Page HC-B(3,5)( )( )-2( ) Propeller Assembly... Figure Steel Hub Unit... Figure HC-B(3,4,5)( )( )-3( ) Propeller Assembly... Figure Start Lock Unit on HC-B(3,4,5)( )( )-3( ) Propeller Assembly... Figure HC-B(3,4)( )( )-5( ) Propeller Assembly with One-piece Spinner Mounting Plate (Superseded Configuration)... Figure HC-B3( )( )-5( ) Propeller Assembly with Two-piece Spinner Mounting Plate (New Configuration)... Figure HC-B(4,5)( )( )-5( ) Propeller Assembly with Two-piece Spinner Mounting Plate (New Configuration)... Figure HC-A3VF-7( ) Propeller Assembly... Figure HC-A3MVF-7( ) and HC-B3TF-7( ) Propeller Assembly... Figure Governor in Onspeed Condition... Figure Governor in Underspeed Condition... Figure Governor in Overspeed Condition... Figure Feathering Governor... Figure Synchronizer/Synchrophaser Governor... Figure Mounting Bolt and Washer... Figure TABLE OF CONTENTS Page 31 Rev. 12 Mar/13

14 Propeller Owner's Manual LIST OF ILLUSTRATIONS Page Installing Propeller on Engine Flange... Figure Diagram of Torquing Sequence for Propeller Mounting Bolts... Figure Determining Torque Value When Using Torquing Adaptor... Figure Beta System Puller for Decompressing -3 Series External Beta System... Figure Carbon Block and Beta Ring Clearance... Figure Carbon Block Assembly... Figure Hub-to-Spacer O-ring Location in the Spacer... Figure Installing the HC-B(3,4)( )W-3( ) Propeller on the Engine Flange... Figure Installing the Washer on the Mounting Stud... Figure One-piece Spinner Mounting Plate Installation... Figure Beta Valve System... Figure Cross Section View of the Beta Valve System... Figure ( ) Propeller Assembly... Figure Spring Assembly to Cylinder Attachment Details... Figure Piston to Link Arm Attachment Details... Figure Filed Rod for Set Screw... Figure Checking Blade Track... Figure Blade Play... Figure Turbine Engine Overspeed Limits... Figure Turbine Engine Overtorque Limits... Figure TABLE OF CONTENTS Page 32

15 5. General (2) Review the propeller and aircraft type certificate data sheet (TCDS), Pilot Operating Handbook (POH), and any applicable Airworthiness Directives for specific information. A. Personnel Requirements (1) Inspection, Repair, and Overhaul (a) Compliance to the applicable regulatory requirements established by the Federal Aviation Administration (FAA) or foreign equivalent is mandatory for anyone performing or accepting responsibility for any inspection and/or repair and/or overhaul of any Hartzell Propeller Inc. product. (b) Personnel performing maintenance on steel hub propellers are expected to have sufficient training and certifications (when required by the applicable Aviation Authority) to accomplish the work required in a safe and airworthy manner. B. Maintenance Practices (1) The propeller and its components are highly vulnerable to damage while they are removed from the engine. Properly protect all components until they are reinstalled on the engine. (2) Never attempt to move the aircraft by pulling on the propeller. (3) Avoid the use of blade paddles. Do not place the blade paddle in the area of the de-ice boot when applying torque to a blade assembly. Place the blade paddle in the thickest area of the blade, just outside of the de-ice boot. Use one blade paddle per blade. (4) Use only the approved consumables, e.g., cleaning agents, lubricants, etc. (5) Safe Handling of Paints and Chemicals (a) Always use caution when handling or being exposed to paints and/or chemicals during propeller overhaul and maintenance procedures. (b) Before using paint or chemicals, always read the manufacturer s label on the container and follow specified instructions and procedures. INTRODUCTION Page 1-5 Rev. 12 Mar/13

16 (c) Refer to the product s Material Safety Data Sheet (MSDS) for detailed information about physical properties, health, and physical hazards of any chemical. (6) Observe applicable torque values during maintenance. (7) Before installing the propeller on the engine, the propeller must be statically balanced. New propellers are statically balanced at Hartzell Propeller Inc. Overhauled propellers must be statically balanced by a certified propeller repair station with the appropriate rating before return to service. NOTE: Dynamic balance is recommended, but may be accomplished at the discretion of the operator, unless specifically required by the airframe or engine manufacturer. Dynamic balancing is to be accomplished in accordance with the procedures and limitations in Maintenance Practices chapter of this manual. Additional procedures may be found in the aircraft maintenance manual. (8) As necessary, use a soft, non-graphite pencil or crayon to make identifying marks on components. (9) As applicable, follow military standard NASMS33540 for safety wire, safety cable, and cotter pin general practices. Use inch (0.81 mm) diameter stainless steel safety wire unless otherwise indicated. INTRODUCTION Page 1-6

17 WARNING: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS MANUAL. INFORMATION CONTAINED IN THIS MANUAL MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. FAILURE TO COMPLY WITH THIS MANUAL OR THE USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/ OR SUBSTANTIAL PROPERTY DAMAGE. FOR THE MOST RECENT REVISION LEVEL OF THIS MANUAL, REFER TO THE HARTZELL PROPELLER INC. WEBSITE AT (10) The information in this manual revision supersedes data in all previous published revisions of this manual. (11) The airframe manufacturer s manuals should be used in addition to the information in this manual due to possible special requirements for specific aircraft applications. (12) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Manual 180 ( ) - Propeller Ice Protection System Manual (b) Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual INTRODUCTION Page 1-7

18 (13) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (14) Approved corrosion protection followed by approved paint must be applied to all aluminum blades. For information concerning the application of corrosion protection and paint, refer to the Maintenance Practices chapter of this manual. Operation of blades without the specified coatings and finishes, i.e., polished blades, is not permitted. C. Continued Airworthiness (1) Operators are urged to stay informed of Airworthiness information using Hartzell Propeller Inc. Service Bulletins and Service Letters that are available from Hartzell Propeller Inc. distributors, or from the Hartzell Propeller Inc. factory by subscription. Selected information is also available on the Hartzell Propeller Inc. website at D. Propeller Critical Parts (1) The following maintenance procedures may involve propeller critical parts. These procedures have been substantiated based on Engineering analysis that expects this product will be operated and maintained using the procedures and inspections provided in the Instructions for Continued Airworthiness (ICA) for this product. Refer to the Illustrated Parts List chapter of the applicable maintenance manual for the applicable propeller model for the identification of specific Critical Parts. (2) Numerous propeller system parts can produce a propeller Major or Hazardous effect, even though those parts may not be considered as Critical Parts. The operating and maintenance procedures and inspections provided in the ICA for this product are, therefore, expected to be accomplished for all propeller system parts. INTRODUCTION Page 1-8

19 6. Reference Publications A. Hartzell Propeller Inc. Publications NOTE: The following publications are referenced within this manual: Active Hartzell Propeller Inc. Service Bulletins, Service Letters, Service Instructions, and Service Advisories. Hartzell Propeller Inc. Manual No. 118F ( ) - Three and Four-Blade Steel Hub Turbine Propeller Maintenance Manual Hartzell Propeller Inc. Manual No. 127 ( ) - Metal Spinner Assembly Maintenance Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 132A ( ) - Five-Blade Steel Hub Turbine Propellers Hartzell Propeller Inc. Manual No. 133C ( ) - Aluminum Propeller Blade Maintenance Manual Hartzell Propeller Inc. Manual No. 159 ( ) - Application Guide - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual 165A ( ) - Illustrated Tool and Equipment Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 180 ( ) - Propeller Ice Protection System Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 181 ( ) - Propeller Ice Protection System Component Maintenance Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual - Available on the Hartzell Propeller Inc. website at INTRODUCTION Page 1-9

20 7. Definitions Hartzell Propeller Inc. Manual No. 202A ( ) - Standard Practices Manual, Volumes 1 through 11 (Volume 7, Consumable Materials is available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Service Letter HC-SL-61-61Y - Overhaul Periods and Service Life Limits for Hartzell Propellers Inc. Aviation Components - Propellers, Governors, and Propeller Damper Assemblies - Available on the Hartzell Propeller Inc. website at A basic understanding of the following terms will assist in maintaining and operating Hartzell Propeller Inc. propeller systems. Term Definition Annealed Softening of material due to overexposure to heat Blade Angle Measurement of blade airfoil location described as the angle between the blade airfoil and the surface described by propeller rotation Brinelling A depression caused by failure of the material in compression Chord A straight line distance between the leading and trailing edges of an airfoil Cold Rolling Compressive rolling process for the retention area of single shoulder blades that provides improved strength and resistance to fatigue Constant Force A force that is always present in some degree when the propeller is operating Constant Speed A propeller system that employs a governing device to maintain a selected engine RPM INTRODUCTION Page 1-10

21 Term Definition Corrosion Gradual material removal or deterioration due to chemical action Crack Irregularly shaped separation within a material, sometimes visible as a narrow opening at the surface Depression Surface area where the material has been compressed but not removed Distortion Alteration of the original shape or size of a component Erosion Gradual wearing away or deterioration due to action of the elements Exposure Leaving material open to action of the elements Feathering The capability of blades to be rotated parallel to the relative wind, thus reducing aerodynamic drag Gouge Surface area where material has been removed Hazardous Propeller... The hazardous propeller effects Effect are defined in Title 14 CFR section 35.15(g)(1) Horizontal Balance.... Balance between the blade tip and the center of the hub Impact Damage Damage that occurs when the propeller blade or hub assembly strikes, or is struck by, an object while in flight or on the ground Major Propeller Effect.. The major propeller effects are defined in Title 14 CFR section 35.15(g)(2) Nick Removal of paint and possibly a small amount of material INTRODUCTION Page 1-11

22 Term Definition Onspeed Condition in which the RPM selected by the pilot through the propeller control lever and the actual engine (propeller) RPM are equal Overhaul The periodic disassembly, inspection, repair, refinish, and reassembly of a propeller assembly to maintain airworthiness Overspeed Condition in which the RPM of the propeller or engine exceeds predetermined maximum limits; the condition in which the engine (propeller) RPM is higher than the RPM selected by the pilot through the propeller control lever Overspeed Damage... Damage that occurs when the propeller hub assembly rotates at a speed greater than the maximum limit for which it is designed Pitch Same as Blade Angle Pitting Formation of a number of small, irregularly shaped cavities in surface material caused by corrosion or wear Propeller Critical Parts. A part on the propeller whose primary failure can result in a hazardous propeller effect, as determined by the safety analysis required by Title 14 CFR section Reversing The capability of rotating blades to a position to generate reverse thrust to slow the aircraft or back up Scratch Same as Nick INTRODUCTION Page 1-12

23 Term Definition Single Acting Hydraulically actuated propeller that utilizes a single oil supply for pitch control Superseded Parts that are considered airworthy for continued flight but may no longer be available Synchronizing Adjusting the RPM of all the propellers of a multi-engine aircraft to the same RPM Synchrophasing A form of propeller sychronization in which not only the RPM of the engines (propellers) are held constant, but also the position of the propellers in relation to each other Track In an assembled propeller, a measurement of the location of the blade tip with respect to the plane of rotation, used to verify face alignment and to compare blade tip location with respect to the locations of the other blades in the assembly Underspeed The condition in which the actual engine (propeller) RPM is lower than the RPM selected by the pilot through the propeller control lever Variable Force A force that may be applied or removed during propeller operation Vertical Balance Balance between the leading and trailing edges of a two-blade propeller with the blades positioned vertically Windmilling The rotation of an aircraft propeller caused by air flowing through it while the engine is not producing power INTRODUCTION Page 1-13

24 8. Abbreviations Abbreviation Term AMM Aircraft Maintenance Manual AN Air Force-Navy (or Army-Navy) AOG Aircraft on Ground FAA Federal Aviation Administration FT-Lb Foot-Pound ICA Instructions for Continued Airworthiness ID Inside Diameter In-Lb Inch-Pound IPS Inches Per Second Lbs Pounds MIL-X-XXX Military Specification MPI Major Periodic Inspection (Overhaul) MS Military Standard MSDS Material Safety Data Sheet OD Outside Diameter NAS National Aerospace Standards NASM National Aerospace Standards, Military N m Newton-Meters POH Pilot s Operating Handbook PSI Pounds per Square Inch RPM Revolutions per Minute TBO Time Between Overhaul TC Type Certificate TSN Time Since New TSO Time Since Overhaul NOTE: TSN/TSO is considered as the time accumulated between rotation and landing, i.e., flight time. INTRODUCTION Page 1-14 Rev. 11 Jul/12

25 INSTALLATION AND REMOVAL - CONTENTS 1. Tools, Consumables, and Expendables A. Tooling B. Consumables C. Expendables Pre-Installation A. Inspection of Shipping Package B. Uncrating C. Inspection after Shipment D. Reassembly of a Propeller Disassembled for Shipment Propeller Assembly Installation A. Precautions B. Installing HC-B(3, 5)( )( )-2( ) Propeller on the Aircraft Engine C. Installing HC-B(3,4,5)( )(A,N,P)-3( ) Propeller on the Aircraft Engine D. Installing HC-B(3,4)( )W-3( ) Propeller on the Aircraft Engine E. Installing HC-B(3,4)( )( )-5( ) Propeller, with a One-piece Spinner Mounting Plate, on the Aircraft Engine F. Installing HC-B(3,4,5)( )( )-5( ) Propeller, with a Two-piece Spinner Mounting Plate, on the Aircraft Engine G. Installing HC-( )3( )( )-7( ) Propeller on the Allison Engine Spinner Dome Installation Post-Installation Checks Spinner Dome Removal Propeller Assembly Removal A. Removal of HC-B(3,5)( )( )-2( ) Propellers B. Removal of HC-B(3,4,5)( )(A,N,P)-3( ) Propellers C. Removal of HC-B(3,4)( )W-3( ) Propellers D. Removal of HC-B(3,4,5)( )( )-5( ) Propellers E. Removal of HC-( )3( )( )-7( ) Propellers F. Removal of Beta Valve Assembly for HC-( )3( )( )-7( ) Propellers Page 3-1

26 INSTALLATION AND REMOVAL - FIGURES Mounting Bolt and Washer... Figure Installing Propeller on Engine Flange... Figure Diagram of Torquing Sequence for Propeller Mounting Bolts... Figure Determining Torque Value When Using Torquing Adaptor... Figure Beta System Puller for Decompressing -3 Series External Beta System... Figure Carbon Block and Beta Ring Clearance... Figure Carbon Block Assembly... Figure Hub-to-Spacer O-ring Location in the Spacer... Figure Installing the HC-B(3,4)( )W-3( ) Propeller on the Engine Flange... Figure Installing the Washer on the Mounting Stud... Figure One-piece Spinner Mounting Plate Installation... Figure Beta Valve System... Figure Cross Section View of the Beta Valve System... Figure ( ) Propeller Assembly... Figure Spring Assembly to Cylinder Attachment Details... Figure Piston to Link Arm Attachment Details... Figure Filed Rod for Set Screw... Figure INSTALLATION AND REMOVAL - TABLES Propeller/Engine Flange O-rings... Table Propeller Mounting Hardware... Table Torque Table... Table Page 3-2

27 1. Tools, Consumables, and Expendables The following tools, consumables, and expendables will be required for propeller removal or installation: A. Tooling Each propeller model requires a calibrated torque wrench, safety wire pliers (alternate: safety cable tool), and the model specific tooling listed below: HC-B3( )(A,N,P)-2( ) Torque wrench adaptor (Hartzell Propeller Inc. P/N AST-2877) 5/8 inch deep well socket 1-7/16 inch crowfoot wrench HC-B(3,4,5)( )(A,N,P)-3( ) Torque wrench adaptor (Hartzell Propeller Inc. P/N AST-2877) 5/8 inch deep well socket 1-7/16 inch crowfoot wrench Feeler gage Beta system puller (Hartzell Propeller Inc. P/N CST-2987) HC-B(3,4)( )W-3( ) Torque wrench adaptor (Hartzell Propeller Inc. P/N AST-3175) Torque check tool (Hartzell Propeller Inc. P/N AST ) Feeler gage Beta system puller (Hartzell Propeller Inc. P/N CST-2987) 5/8 inch deep well socket 1-7/16 inch crowfoot wrench HC-B5M( )-2 HC-B(3,4,5)( )-5( ) Torque wrench adaptor (Hartzell Propeller Inc. P/N AST-2877) One inch deep well socket 1-13/16 inch crowfoot wrench Page 3-3

28 HC-( )3( )F-7( ) Torque wrench adaptor (Hartzell Propeller Inc. P/N AST-2917) 5/8 inch deep well socket 1-7/16 inch crowfoot wrench B. Consumables Quick Dry Stoddard Solvent or Methyl-Ethyl-Ketone (MEK) Anti-Seize Compound (MIL-PRF-83483) C. Expendables inch (0.81 mm) Stainless Steel Aircraft Safety Wire (Alternate: inch [0.81 mm] aircraft safety cable and associated hardware) O-ring, propeller flange (see Table 3-1) O-ring, for HC-B(3,4)( )W-3( ) spacer (see Table 3-1) Page 3-4

29 A Flange W10107C W10107B W10108C W10109C W10109B SEQUENCE A SEQUENCE B Use Sequence A for steps one and two. Use Sequence B for step three. Step 1 - Torque all bolts to 40 ft-lbs (54 N m). Step 3 - Torque all bolts to Step 2 - Torque all bolts to 80 ft-lbs (108 N m). Table 3-3. F Flange Step 1 - Torque all bolts to 40 ft-lbs (54 N m). Step 2 - Torque all bolts to Table 3-3. N, P or W Flange SEQUENCE A Use Sequence A for steps one and two. SEQUENCE B Use Sequence B for step three. Step 1 - Torque all bolts to 40 ft-lbs (54 N m). Step 3 - Torque all bolts to Step 2 - Torque all bolts to 80 ft-lbs (108 N m). Table 3-3. Diagram of Torquing Sequence for Propeller Mounting Bolts Figure 3-3 Page 3-11 Rev. 8 Dec/06

30 (7) Install the mounting bolts with washers through the engine flange and into the propeller hub flange. Refer to Figure 3-2. (8) Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling in this chapter) to torque all mounting bolts in sequences and steps shown in Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value. (9) Safety all mounting bolts with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two bolts per safety.) CAUTION: A flange mounting bolts F flange mounting bolts TO FACILITATE BOXING AND SHIPPING OF PROPELLERS, THE PISTON NUT (A-880-1) ON HC-B3( )( )-2( ) STEEL HUB TURBINE PROPELLERS MAY HAVE BEEN REMOVED TO ALLOW ROTATING OF THE BLADES BEFORE PACKAGING Ft-Lbs ( N m) wet Ft-Lbs ( N m) N/P flange mounting bolts W flange mounting nuts Spinner mounting bolts Piston nut (lock nut) Guide rod jam nuts Lubrication Fitting Check Nut (beta valve assembly) Ft-Lbs ( N m) wet Ft-Lbs ( N m) Ft-Lbs (41-54 N m) 120 Ft-Lbs (163 N m)* 10 Ft-Lbs (14 N m)* 4 Ft-Lbs (5 N m)* 9-11 Ft-Lbs (12-15 N m) * Torque tolerance is ± 10 percent unless otherwise noted. NOTE 1: Torque values are based on non-lubricated threads, unless otherwise specified. NOTE 2: Wet torque values denote the use of anti-seize compound MIL-PRF Torque Table Table 3-3 Page 3-12

31 CAUTION: ID CHAMFER OF THE WASHER MUST BE FACING TOWARD THE BOLT HEAD. WASHERS WITHOUT CHAMFER MUST BE INSTALLED WITH ROLLED EDGES TOWARD THE BOLT HEAD. (REFER TO FIGURE 3-1). (8) Install mounting bolts with washers through the engine flange and into the propeller hub flange. Refer to Figure 3-2. (9) Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling in this chapter) to torque all mounting bolts in sequences and steps shown in Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value. (10) Safety all mounting bolts with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two bolts per safety). (11) Decompress the external beta system and remove the beta system puller. CAUTION: THE BETA RING MUST NOT CONTACT ANY ENGINE COMPONENT OR MOUNTING BOLT SAFETY WIRE. THE BETA SYSTEM COULD BE DAMAGED IF IT CONTACTS ANY STATIC ENGINE COMPONENT WHILE ROTATING. (12) Examine the beta ring to make sure that it is not in contact with any engine component or mounting bolt safety wire. (a) If there is contact between the beta ring and any engine component or mounting bolt safety wire, consult qualified personnel at an appropriately licensed propeller repair facility. (13) Install the carbon block into the beta linkage lever in accordance with the airframe manufacturer s instructions. Page 3-17

32 Snap Ring Carbon Block Assembly Side clearance to inch (0.03 to 0.25 mm) upon installation. Beta Ring APS0168b Carbon Block and Beta Ring Clearance Figure 3-6 Snap Ring Yoke Unit Cotter Pin Beta Lever Clevis Pin Block Unit BPS0041 Carbon Block Assembly Figure 3-7 Page 3-18

33 CAUTION 1: FIT THE BLOCK IN THE BETA RING WITH A MINIMUM SIDE CLEARANCE OF INCH (0.03 mm). REFER TO FIGURE 3-6. CAUTION 2: MAXIMUM SIDE CLEARANCE PERMITTED IS INCH (0.25 mm) IN ACCORDANCE WITH THE CARBON BLOCK ASSEMBLIES SECTION IN THE MAINTENANCE PRACTICES CHAPTER OF THIS MANUAL. (14) Install the carbon block assembly (Figure 3-7) into the beta ring. (15) Install, adjust and safety the beta linkage per the airframe manufacturer s instructions. CAUTION: TO FACILITATE BOXING AND SHIPPING OF PROPELLERS, THE PISTON NUT MAY HAVE BEEN REMOVED TO ALLOW ROTATING OF THE BLADES BEFORE PACKAGING. (16) Procedure for reinstallation of piston nut, if applicable. (a) Following the installation of the propeller, use a breaker bar and a 5/8 inch deep well socket to hold the pitch change rod. (b) Using a 1-7/16 inch crowfoot wrench and torque wrench, torque the A piston nut. Refer to Table 3-3 and Figure 3-4 for the proper torque value. NOTE: The removal and subsequent reinstallation of the piston nut does not require that the propeller blade angles be re-checked. (17)If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Manual 180 ( ) - Propeller Ice Protection System Manual Page 3-19 Rev. 11 Jul/12

34 (b) Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (18) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). D. Installing HC-B(3,4)( )W-3( ) Propeller on the Aircraft Engine CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. CAUTION 2: WHEN INSTALLING THE HC-B4TW-3/T10282N PROPELLER ON THRUSH AIRCRAFT MODELS S2R-H80 OR S2RHG-H80, COMPLIANCE WITH GE AVIATION SERVICE BULLETIN H IS REQUIRED. (1) Use a beta system puller CST-2987 (Figure 3-5) to compress the beta system and pull the beta ring forward to allow access to the propeller mounting flange. Page 3-20

35 WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. CAUTION: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (2) With a suitable crane hoist and sling, carefully move the propeller assembly to the aircraft engine mounting flange. CAUTION: IF THE PROPELLER IS REMOVED BETWEEN OVERHAUL INTERVALS, A TORQUE CHECK OF THE MOUNTING STUDS MUST BE PERFORMED. (3) Unless this is the first installation of a new, or newly overhauled propeller, perform a torque check of the propeller mounting studs as follows: (a) Thread the torque check tool AST onto each propeller mounting stud and torque to 35 ft-lbs (47.6 N m). (b) Visually inspect each stud for evidence of movement. (c) Remove the torque check tool AST while visually inspecting each stud for evidence of movement. (d) If any stud rotates due to either the tightening or removal of the torque check tool, all studs must be replaced. Refer to Hartzell Propeller Inc. Standard Practices Manual 202A (ATA ) for stud replacement procedures. (4) Make sure the propeller hub flange and the engine flange mating surfaces are clean. (5) Install the specified O-ring on the engine flange. Refer to Table 3-1. (6) If the C spacer is attached to the propeller hub with screws, proceed to step 3.D.(8). Page 3-21

36 (7) If the C spacer is not already installed on the propeller hub perform the following installation procedures: (a) If the hub flange does not have two 8-32 threaded holes to attach the spacer or, if two attachment screws were not provided, perform the following steps: 1 Coat the hub-to-spacer O-ring with grease. Refer to Table Install the hub-to-spacer O-ring in the groove in the spacer that interfaces with the face of the hub flange. Refer to Figure Align the mounting studs and dowel pin holes in the propeller hub flange with the mounting holes and dowel pins in the spacer. W10409 W10410 Attachment screw hole Dowel pin Dowel pin O-ring groove Engine Side Propeller Side Engine Side Dowel pin Attachment screw hole Hub-to-Spacer O-ring Location in the Spacer Figure 3-8 Dowel pin Page 3-22

37 CAUTION: MAKE SURE THE HUB-TO-SPACER O-RING STAYS IN THE GROOVE IN THE SPACER. IF THE O-RING IS TWISTED OR PINCHED, OIL LEAKAGE WILL RESULT WHEN THE PROPELLER IS OPERATED ON THE AIRCRAFT. 4 Slide the spacer onto the mounting studs and against the hub flange. NOTE: If the propeller installation will be delayed, the spacer and O-ring should be installed and temporarily held in place with non-self locking nuts and a sufficient number of washers on at least two mounting studs. Remove the nuts and washers before installation. (b) If the hub flange has two 8-32 threaded holes and two MS24693-S2 flat-head screws (HPI P/N B-3868-S52) are provided to attach the C spacer, perform the following steps: 1 Coat the hub-to-spacer O-ring with grease. Refer to Table Install the hub-to-spacer O-ring in the groove in the spacer that interfaces with the face of the hub flange. Refer to Figure Align the spacer attachment holes with the two 8-32 threaded holes in the hub flange. CAUTION: MAKE SURE THE HUB-TO-SPACER O-RING STAYS IN THE GROOVE IN THE SPACER. IF THE O-RING IS TWISTED OR PINCHED, OIL LEAKAGE WILL RESULT WHEN THE PROPELLER IS OPERATED ON THE AIRCRAFT. 4 Slide the spacer onto the mounting studs and against the hub flange. Page 3-23

38 APS6160C.TIF E-7373i.PLT, W10079 Torque Wrench Hub-to-Engine O-ring Washer Propeller Flange Hub-to-Spacer O-ring Torque Wrench Adaptor* Nut Engine Flange Screw *Note: If torque wrench adaptor is used, use the calculation in Figure 3-4 to determine correct torque wrench setting. Dowel Pin Holes (4) (Unthreaded) W Propeller Flange Spinner Mounting Plate Attachment Holes (10) (Threaded) Spacer Attachment Holes (2) (Threaded), If Present Mounting Studs (8) Installing the HC-B(3,4)( )W-3( ) Propeller on the Engine Flange Figure 3-9 Page 3-24 Rev. 11 Jul/12

39 5 Insert supplied flat-head screw through each screw hole in the spacer and into the 8-32 threaded holes in the hub flange. Refer to Figure 3-9. CAUTION: MAKE SURE THE FLAT-HEAD ATTACHMENT SCREWS DO NOT PROTRUDE ABOVE THE ENGINE- SIDE SURFACE OF THE SPACER. 6 Tighten the flat-head screw until snug. 7 If after the flat-head screws are tightened, one or both are protrude above the engine side surface of the spacer, perform the following steps: a Remove both flat-head screws and the spacer. b Rotate the spacer 180 degrees, aligning the screw holes in the spacer with the 8-32 threaded holes in the hub flange. CAUTION: MAKE SURE THE FLAT-HEAD ATTACHMENT SCREWS DO NOT PROTRUDE ABOVE THE ENGINE- SIDE SURFACE OF THE SPACER. c Slide the spacer onto the mounting studs and against the hub flange. d Insert a flat-head screw through each screw hole in the spacer and into the 8-32 threaded holes in the hub flange. Refer to Figure 3-9. e Tighten the flat-head screw until snug. f If after the flat-head screws are tightened, one or both are protrude above the engine side surface of the spacer, remove the screws. NOTE: If the propeller installation will be delayed, the spacer and O-ring should be installed and temporarily held in place with nonself locking nuts and a sufficient number of washers on at least two mounting studs. Remove the nuts and washers before installation. Page 3-25 Rev. 11 Jul/12

40 CAUTION 1: MAKE SURE THAT COMPLETE AND TRUE SURFACE CONTACT IS ESTABLISHED BETWEEN THE SPACER AND THE ENGINE FLANGE. CAUTION 2: IF THE C SPACER IS NOT ATTACHED TO THE HUB, MAKE SURE THE HUB-TO-SPACER O-RING STAYS IN THE GROOVE IN THE SPACER. IF THE O-RING IS TWISTED OR PINCHED, OIL LEAKAGE WILL RESULT WHEN THE PROPELLER IS OPERATED ON THE AIRCRAFT. (8) Slide the propeller onto the engine flange. OD Chamfer Engine Flange Washer Stud Engine Shaft Fillet W10411 Installing the Washer on the Mounting Stud Figure 3-10 Page 3-26

41 CAUTION 1: NEW PROPELLER MOUNTING NUTS MUST BE USED WHEN INITIALLY INSTALLING A NEW OR OVERHAULED PROPELLER. CAUTION 2: THE SIDE OF THE WASHER WITH THE OD CHAMFER MUST BE AGAINST THE ENGINE FLANGE. REFER TO FIGURE (9) Install self locking mounting nuts with washers onto the propeller mounting studs. Refer to Table 3-2 for appropriate mounting hardware. Refer to Figure NOTE 1: The OD chamfer on the washer is for clearance of the engine flange fillet. Refer to Figure NOTE 2: If the propeller is removed between overhaul intervals, mounting nuts and washers may be reused if they are not damaged or corroded. (10) Use a torque wrench and the specified torque wrench adaptor (see paragraph 1.A. Tooling in this chapter) to torque all mounting nuts in the sequences and steps shown in Figure 3-3. Refer to Table 3-3 and Figure 3-4 to determine the proper torque value. (11) Safety all propeller mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two bolts per safety.) (12) Decompress the external beta system and remove the beta system puller. CAUTION: THE BETA RING MUST NOT CONTACT ANY ENGINE COMPONENT OR MOUNTING BOLT SAFETY WIRE. THE BETA SYSTEM COULD BE DAMAGED IF IT CONTACTS ANY STATIC ENGINE COMPONENT WHILE ROTATING. (13) Examine the beta ring to make sure that it is not in contact with any engine components or mounting bolt safety wire. Page 3-27

42 (a) If there is contact between the beta ring and any engine components or mounting bolt safety wire, consult qualified personnel at an appropriately licensed propeller service facility. (14) Install the carbon block into the beta linkage lever per the airframe manufacturer s instructions. CAUTION 1: FIT THE BLOCK IN THE BETA RING WITH A SIDE CLEARANCE OF INCH (0.03 mm). REFER TO FIGURE 3-6. CAUTION 2: MAXIMUM SIDE CLEARANCE PERMITTED IS INCH (0.25 mm) IN ACCORDANCE WITH THE CARBON BLOCK ASSEMBLIES SECTION IN THE MAINTENANCE PRACTICES CHAPTER OF THIS MANUAL. (15) Install the carbon block assembly (Figure 3-7) into the beta ring. (16) Install, adjust and safety the beta linkage per the airframe manufacturer s instructions. CAUTION: TO FACILITATE BOXING AND SHIPPING OF THE PROPELLER, THE PISTON NUT MAY HAVE BEEN REMOVED TO ALLOW ROTATING OF THE BLADES BEFORE PACKAGING. (17) Procedure for reinstallation of the piston nut, if applicable. (a) Following the installation of the propeller, use a breaker bar and a 5/8 inch deep well socket to hold the pitch change rod. (b) Using a 1-7/16 inch crowfoot wrench and torque wrench, torque the A piston nut. Refer to Table 3-3 and Figure 3-4 for the proper torque value. NOTE: The removal and subsequent reinstallation of the piston nut does not require that the propeller blade angles be re-checked. Page 3-28

43 (18)If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Manual 180 ( ) - Propeller Ice Protection System Manual (b) Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (19) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). Page 3-29

44 SPINNER BULKHEAD START LOCKS PROPELLER HUB FLANGE SPINNER MOUNTING PLATE SPINNER BULKHEAD AND START LOCKS ATTACHMENT BOLTS W10103 SPINNER BULKHEAD ENGINE FLANGE START LOCKS SPINNER MOUNTING PLATE SCALLOPS SPINNER MOUNTING PLATE One-piece Spinner Mounting Plate Installation Figure 3-11 Page 3-30 Rev. 11 Jul/12

45 E. Installing HC-B(3,4)( )( )-5( ) Propeller, with a One-piece Spinner Mounting Plate, on the Aircraft Engine CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. NOTE: Some -5 propellers were previously manufactured with a one-piece spinner mounting plate. The spinner bulkhead, which has start locks mounted on it, is attached to the spinner mounting plate. The spinner mounting plate is installed in a cutaway portion of the propeller hub flange and is pinched between the propeller hub flange and the engine flange. Refer to Figure WARNING: CAUTION: MAKE SURE THE SLING IS RATED UP TO 800 LBS (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (1) With a suitable crane hoist and sling, carefully move the propeller assembly to the aircraft engine mounting flange. (2) Make sure the propeller hub flange and engine flange mating surfaces are clean. (3) Install the specified O-ring on the engine flange. Refer to Table 3-1. Page 3-31

46 (4) Retract each start lock pin and hold into place with a heavy wire inserted into the hole in each auto high pitch housing. (5) Slide the assembled one-piece spinner mounting plate, spinner bulkhead and start lock onto the propeller hub flange. (a) The start locks must face toward the propeller. (6) Align the clearance scallops in the spinner mounting plate with the holes in the propeller hub flange. Refer to Figure NOTE: This will insure that the spinner mounting plate does not interfere with the mounting bolts and dowel pins. (7) Align the start locks with each blade and clamp mounted stop plate. NOTE: The start locks are attached to the spinner bulkhead. (8) Align mounting and dowel pin holes in the propeller hub flange with the mounting holes and dowel pins in the engine flange. CAUTION: MAKE SURE THAT COMPLETE AND TRUE SURFACE CONTACT IS ESTABLISHED BETWEEN THE PROPELLER HUB FLANGE AND THE ENGINE FLANGE. (9) Slide the propeller flange onto the engine flange. CAUTION: NEW PROPELLER MOUNTING BOLTS MUST BE USED WHEN INITIALLY INSTALLING A NEW OR OVERHAULED PROPELLER. (10) Apply MIL-PRF anti-seize compound to the threaded surfaces of the mounting bolts. Refer to Table 3-2 for appropriate mounting hardware. NOTE: If the propeller is removed between overhaul intervals, mounting bolts and washers may be reused if they are not damaged or corroded. Page 3-32